Aircraft



Oct. 25, 1932. a. J. E. KROOK ET AL 1,883,970

AIRCRAFT Filed May 5, 1931 2 Sheets-Sheet 1 Jakob EYus 'ws Kroo'i Johannefi Hafden' NVENTOR5 Get. 25, 1932. B. J. E. KROOK ET AL I 1,883,970

AIRCRAFT Filed M y 5, 1931 2 Sheets-Sheet 2 BerncH' Soflob Erasmg s K an may.

l atented Oct. 2 5, 1932 UNITED STATES PATENT VOFFICE BERNIDT J'AKOB ERASMUS KROOK, OF STOCKHOLM, AND JOHANNES HARDE'N, OF

LIDINGO, SWEDEN I AIRCRAFT Application filed May 5, 1931, Serial No. 535,130, and in Sweden Ma 6, 1930.

When covering with fog, spreading of gases and the like fromair-craft the following main points are very important. The apparatus should be light in proportion to the volume of the gas supplying substance, which it is able to give off. The filling, transport and quick mounting of the apparatus on the aircraft should be easily effected. Further it should be securely controlled from the aircraft, even during aggravating circumstances occurring during the flying without unnecessarily encumbering the crew with extra labour. Moreover it should have such a form and such a location so as'not to hinder the movements of the air-craft. Finally the spreading member of the apparatus should be formed in such a way that the highest possible spreading effect is obtained without the ejected gases influencing either the crew or the air-craft.

The present invention relates to such an apparatus for producing fog and spreading of gases from air-craft through which the above-mentioned requirements are filled, and it is substantially characterized thereby that the fog or gas producing material is enclosed in a receptacle which is arranged outside the aircraft, preferably below thesame so as to be pivoted or tilted, and from which the fog-producing or gas-spreading material is ejected into the air through a spreading member.

An embodiment of the invention is illustrated in the accompanying drawings, in

V which I. receptacle 1, preferably a metal cylinder, of

a torpedo or streamline form. The receptacle 1 is by means of a pivot 2 located in a suspension device 3, so as to be turned or tilted, said suspension device being permanently secured between the landing and float-gauge stay respectively. By pulling out the pivot 2 the receptacle is adapted to be detached and exchanged. The receptacle is balanced in such away that its centre; of gravity is located behind the shaft, and thus its narrower rear end, on account of the gravity, aims at moving downwards. It is held in its normal position by means of a thin wire-rope 4, which, over a block (not shown in the drawings) or the like proceeds up to the cabin of the pilot or to that of the observer. H

During transport or under similar circumstances the receptacle is provided with a detachable protecting cap, quite covering the opening of thereceptacle, saidcap being unscrewed and the spreading member being substituted for same when the receptacle is pulled into its position.

The spreading member consists of a paddle shaped device 5, said device being, by means of acasing 6 provided with a screwjoint, adapted to be mounted on to the opening of the receptacle after the cap has been removed. A paddle-shaped shelter 7 to pre- V vent the gases from being spread upward is located above the outlet opening. Between the paddles 5 and 7, said paddles increasing in width outwards counted from the opening, there are two curve-shaped side or partition walls 88 serving as deflection Wings and diverging counted from said opening, whereby the lateral spreading is facilitated.

In the traverse passage of the spreading member said passage being located behind the opening of the receptacle, there is located a shutting 0E member (a lock-paddle or the like), which is adapted to be pulled out, and which is connected to the body of the aircraft by means of the wire-rope 9. When turning the rear portion of the receptacle downward about the pivot 2 by influence of the control line 4 the shutting off member is pulled out on account of the tension arising in the rope 9, by which the material producing the gas or fog is streaming out on the spreading member. The shutting off member can also be arranged automatically pivotable in the form of a valve or the like.

The spreading member is thus located that the air current, arising when the aircraft is in motion,sweeps past and under the edge of the spreading member, whereby a whirl arises which increases the spreading. In order to obtain a further increased spreading effect the exhaust pipes from the engine may be extended under the lower edge of the spreading member, by which the whirls are increased "by" the influence of the exhaust gases. 7

According to the invention also other em bodimentsof the devicethan those described- 7 above may be thought of. The receptacle'l can be thus arranged that the turning shaft of same takes up a position deviating more, or less from the right angle to the longitudinal direction or are aircraft. The outlet opening might also be located on the side portion of the receptacle. Iii'stead" of usth'e ropest and 9' stays, links or the like can be advantageously used.

VThe production or composition ofinaterials intended for producing fog or gas are so'w'ell' known within anotherlin'e of the'technlics', that they need not be more particularly descrfloed in this connection. 4

Having now described our invention, what we claim as new and desire to secure by Letters Patent is i v v 1. In an aircraft, a device for producing fog and spreading gases, comprising a receptacle forthe taking up of the material producing the fog or the gas, said receptacle iaving an opening normally shut and being located outside the body of the, aircraft and being pivotable in such a way that the con tents can be ejected through the opening of the receptacle, and in which the normally shut opening of the receptacle is shut by means of a shutting member, which is automatically opened when the receptacle vis turned; 7 v a t an aircraft, a device forproducing fogand spreading. gases, comprising a re ceptacle for, the taking up of the material producing the fog or the gas, said receptacle havin an opening normally shut andbeing locate dontside the body of theaircraft and being ,pi votable in such a way that the contents can beejected through the opening of receptacle, and in which the opening of the receptacle is provided with a shutting off niembeiy which is connected to the body of the aircraft by means of a rope in such a manner that, when turning the receptacle, said: shutting offinember is opened by means ofthe. tension arising in the rope.

3: In an aircraft,a device for producing reggae spreading gases, comprising a re ceptaclefoi' taking up the material producing the fog or the gas, said receptacle being located outside the body of the aircraft and turnable and provided with an outlet opening, outside of which, opening a spreading member is located, and in which the spreadineinber has the form of a downwards and backwards directed paddle'shaped device provided with curve shaped side-walls for taking up and spreading the ejected material producing the fog or gas, said walls diverging backwards and serving as deflection wings.

4c. In an aircraft, a device for producing fog and spreading gases, comprising a receptalcle for taking up the material producing the fog or the gas, said receptacle being located outside the; body of the aircraft and turnable-and provided with an outlet opening, outside of which opening a spreading member is located, and in which the spreading member is detachably mounted with respam to theopeni'n'g of the receptacle and a protection cap to cover the outlet opening, is provided to be substituted for the'sprea'ding member during transport.

5'. In aircraft, adevice for producing fog and spreading gases, comprising a rec'ep tacle for taking up the material producing the fog or the gas, said receptacle being lo cated outside the body of the aircraft and turna'b'le and provided with an outlet opening, outside of which opening a spreading member located, and in which a paddle shaped shelter is located above the outlet opening, by which the gas is hindered from streaming u ward;

In witness whereof we have hereunto sisn'edour mes-x .p .o a ,i t. Brawn .IAKOB Erasmus noon.

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